Airplane General

  • Passenger (-100/-200)
  • Freighter
  • SP
  • Passenger (-300)

Deck Structure:
  • Passenger (-100/-200)
  • Freighter
  • SP
  • Passenger (-300)

Turning Radius
Cockpit Panels
Flight Crewman Seat
Pilot's Seat Adjustment
Weight and Balance System
Potable Water Preselect System
Side / Nose Cargo Door
Flight Deck Door
Cargo Doors - Indicator

  • Passenger (-100/-200)
  • Freighter
  • SP
  • Passenger (-300)

Deck Structure:
  • Passenger (-100/-200)
  • Freighter
  • SP
  • Passenger (-300)

Turning Radius

Use maximum width available.
Use of minimum width will cause excessive tyre slippage and scrubbing.
Taxi Speed, GW, CG, Runway Conditions and Nose Wheel Steering will affect turn radius and location of turn centre.

Cockpit Panels

First Officer
Pilot's Central Instrument Panel & Lightshield
Flight Engineer's Panel
Captain's & First Officer's Auxiliary Panels
Pilot's Control Stand

Flight Crewman Seat

The Captain's and First Officer's seats are mounted on tracks which permit fore and aft travel of the seat.
Both seats also travel outboard during the last four inches of travel.
Adjustment controls provide for fore and aft travel, vertical travel, seat tilt and backrest recline.
Forward, aft and vertical travel are controlled electrically with manual backup.
Recline and tilt are controlled manually.
Each armrest may be adjusted and the inboard armrests may be folded and stowed to facilitate ingress and egress of the occupant.

The Flight Engineer's seat is also track mounted for fore and aft travel.
The seat is also capable of vertical and lateral travel, backrest adjustment and swivel adjustment to the left.
Forward aft and vertical travel are controlled electrically with manual backup.
Lateral travel and recline adjustment are controlled manually.
The swivel adjustment control handle is located under the forward right corner of the seat bottom.
The seat may be swivelled to the left and locked at 30, 60 or 90 degree positions.
Each armrest may be adjusted and the left armrest may be folded and stowed.

Pilot's Seat Adjustment
First, position the seat vertically until the horizontal reference line is parallel and level with the eye.
Then, adjust the seat fore and aft intil the vertical line passes out of peripheral vision when looking straight ahead through the forward window.
Note: The recline adjustment feature of the seat will be in an optimum position near of slightly aft of full upright position.

- Interior

Pilot's Overhead Panel:

Panel Back Gound Light Switch:

Controls intensity of Captain, F/O and centre panel background lights.

Overhead Light Switch:

Controls intensity of Pilot's overhead panel edge lighting.

Dome Light Switch:

Controls the intensity of Captain and F/O dome lights.

Storm Light Switch:

ON - Overrides background lighting switches to provide full intensity and turns on the dome lights.

Master Indicator Lights Dim and Test Switch:

TEST - Tests all indicator lights on Pilot's panels except:
        approach progress display,
        marker beacon
        INS modules.

Intensity set as desired buy DIM or BRIGHT.

Pilot's Control Stand:

Control Stand Panel Light Switch:
Controls Intensity of lights on Pilot's control stand forward and aft electronic panels.

Center Forward Panel Light Switch:
Controls intensity of edge lighting on Pilot's centre panel.

Pilot's Lightshield:

Pilot's Lightshield Light Switch:

Controls intensity of edge lighting on lightshield

Captain's and F/O's Auxiliary Panels

Digital Light Switch:
Controls intensity of digital displays on Captain & F/O instrument panels respectively.

Map Light Switch:
Pull out and rotate for variable intensity.  Light located in ceiling.

Panel Light Switch:
Controls intensity of edge lighting on Captain & F/O instrument panels respectively.

Clock:  Stop/Start/Reset stopwatch function on clock..

Lighting - Exterior:

Weight and Balance System

General Description:
The weight and balance system utilizes a strain gauge system to provide a direct readout of the airplane total weight and centre of gravity during ground operation.

The system consists of a strain gauge transducer mounted on each landing gear axle (18 in total), an attitude sensor located in the main equipment centre, a computer located in the cockpit and an indicator/control panel at the F/Es station.

The transducers measure only vertical loads.  The output of all transducers in each main landing gear truck are combined into a single channel for the computer.  The nose gear has two channels into the computer.  The attitude sensor provides a slope CG correction to the computer for ramp slope or airplane attitude.  The computer sums the individual axle weights to provide the airplane gross weight in kilograms and calculates CG in units of percentage of mean aerodynamic chord (MAC).

Weight and balance module:

The weight and balance module contains the gross weight and CG readouts in digital form.  The POWER switch turns the system on or off.

The SYSTEM CHECK switch allows the instruments, channels, attitude sensor and alarm circuit to be tested.  A series of lights define the system status. 

The gross weight indicator has a graduated, uncalibrated dial for determining the wind effect.  By observing the dial to determine the average wind and using the read/standby switch to take a reading at that timem the wind error can be reduced or eliminated.

Weight and balance auxiliary panel:
Provides for individual channel selections and inflight zero check and adjustments at the F/E panel.  Also provides for on ground confidence check.

Note:  Adjustments and reading should be within placarded limits.

Weight and Balance Computer:

The weight and balance computer is located on the bottom shelf of the E-11 equipment rack.
If, while checking the system in the CHAN position, a NO GO condition exists, a test switch on the computer allows each channel to be tested and the defective channel isolated.

Using the appropriate OVERRIDE switch on the computer, the corresponding opposite channel may be substituted for the defective channel.
This results in a slightly degraded operational system, since an uneven left-right weight distribution is possible.
For example, if the left wing truck channel is defective, the right wing truck channel output is applied to replace that channel.  After the approriated substitution is made the GO and DEG MODE lights will be illuminated.

Potable Water Preselect System:

The potable water quantity preselect system allows the flight crew to preselect in 1/8 th tank increments the quantity of water that is loaded on board the aircraft. 
The system is controlled by a quantity select switch and a water quantity gauge on the water quantity  indication and select module.

Side / Nose Cargo Door

Exterior and Interior controls.  The door can be operated from inside or outside the aircraft when the latch handle retainer over the interior latch lock handle is released.
Door motion can be stopped or reversed at any point by releasing or repositioning the control switch.

Caution:  Before opening or closing door - check external clearance.  Instal nose door personnel strap.  Remove loose material in area of door.  Alert personnel inside and outside the aircraft.
Main deck cargo handling bus must be powered for NCD operation.  DC Bus #2, Battery & Essential Buses must be powered for annunciation on the F/E's panel.

Flight Deck Door

The flight deck security door meets requirements for resistance to ballistic penetration and intruder entrance.
When the door is closed the door locks when electrical power is available and unlocks when electrical power is removed.
A viewing lens in the door allows observation of the passenger cabin.
The door can be manually opened from the flight deck by turning the door handle.

The door incorporates a deadbolt with a key lock.  Rotating both concentric deadbolt levers to the locked (horizontal) position prevents the passenger cabin key from unlocking the door.  Rotating only the forward deadbolt lever to locked allows the key to unlock the door.

The flight deck access system consists of an emergency access panel, chime module, three position door lock selector, two indicator lights and an access system switch.  The emergency access panel includes a six button keypad for entering the numeric emergency access code along with red, amber and green lights.
The red light illuminates to indicate the door is locked. 
When the correct emergency access code is entered, the amber light illuminates. 
The green light illuminates to indicate the door is unlocked.

The emergency access code is used to gain access to the flight deck in case of pilot incapacitation.  A flight deck chime and illumination of the amber AUTO UNLK light indicates the correct emergency access code has been entered and the door is programmed to unlock after a time delay.  Selecting the DENY position on the door lock selector denies entry and prevents further keypad entry for several minutes.
To allow entry, the selector is turned to the UNLKD position which unlocks the door while held in that position.
Before the door unlocks, the chime sounds continuously and the AUTO UNLK light flashes.

The door latch system incorporates a pressure rate-sensor that unlocks the door in the event of flight deck depressurization.

Cargo Doors - Indicator

Cargo Doors Light (Amber)

ILLUMINATED - Repeater light indicating FWD, AFT or SIDE cargo doors light at the Flight Engineer's panel is illuminated.